Systems and methods to control gain of an electric aircraft are provided in this disclosure. The system may include gain scheduling to provide stability of the electric aircraft at various dynamic states of operation. The system may include a sensor to obtain measurement datum of an operating state. The system may further include a controller that adjusts a control gain of the electric aircraft as a function of the measurement datum. The gain control may be determined by a gain schedule generated by the controller.
Legal claims defining the scope of protection, as filed with the USPTO.
3. The system of claim 1, wherein the measurement datum further comprises a spin speed of a rotor blade of the eVTOL aircraft.
4. The system of claim 1, wherein the measurement datum further comprises a pitch angle of a rotor of the eVTOL aircraft.
5. The system of claim 1, wherein the sensor comprises an inertial measurement unit (IMU).
7. The system of claim 1, wherein the controller comprises an outer loop controller and an inner loop controller.
8. The system of claim 1, wherein the aircraft command comprises a movement of a flight component of the electric aircraft to pitch the aircraft upward by the predetermined angle.
9. The system of claim 1, wherein the electric aircraft is a drone.
12. The method of claim 10, wherein the sensor comprises an inertial measurement unit (IMU).
13. The method of claim 10, wherein the controller comprises an outer loop controller and an inner loop controller.
14. The method of claim 10, wherein the aircraft command comprises a movement of a flight component of the electric aircraft to pitch the aircraft upward by the predetermined angle.
15. The method of claim 10, wherein the electric aircraft is a drone.
16. The method of claim 10, wherein the measurement datum further comprises a spin speed of a rotor blade of the eVTOL aircraft.
17. The method of claim 10, wherein the measurement datum further comprises a pitch angle of a rotor of the eVTOL aircraft.
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October 30, 2021
February 28, 2023
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